S2.253 home
topic index
Engine Model: S2.253. Other Designations: S2.253. Designer: Isayev. Developed in: 1949-55. Application: R-11 (Scud B) 8A61. Propellants: Nitric acid/Kerosene. Thrust(vac): 93.300 kN (20,975 lbf). Thrust(sl): 71.000 kN (15,961 lbf). Isp: 251 sec. Isp (sea level): 219 sec. Burn time: 95 sec. Diameter: 0.96 m (3.14 ft). Chambers: 1. Country: Russia. First Flight: 1953. Last Flight: 1967. Flown: 92.

Thrust 8300 kgf at sea level. Fuel Kerosene T-1, chemical ignition by TG-02.

Engine Model: S2.253 derivative. Other Designations: S2.253 derivative. Designer: Isayev. Application: EKR (experimental winged missile). Propellants: Lox/Kerosene. Thrust(vac): 93.200 kN (20,952 lbf). Isp: 250 sec. Isp (sea level): 217 sec. Burn time: 127 sec. Chambers: 1. Country: Russia. Status: Study 1953.

Derivative of S2.253 was proposed for use in EKR Stage 1 (project for an experimental winged missile).

Engine Model: S2.253A. Other Designations: S2.253A. Designer: Isayev. Developed in: 1953-59. Application: R-11FM. Propellants: Nitric acid/Kerosene. Thrust(vac): 93.000 kN (20,907 lbf). Isp (sea level): 218 sec. Chambers: 1. Oxidizer to Fuel Ratio: 3.76. Country: Russia. Status: Out of Production.

Used in R-11FM submarine version of Scud B. Fuel Kerosene T-1, chemical ignition by TG-02. Mixture ratio derived from tank content. 81 kN sea-level.

S2.253 used on Rocket Stages
Bibliography:

  • Semenov, Yuri P Editor, Raketno-kosmicheskaya korporatsiya 'Energia' imeni S P Koroleva, Moscow, Russia, 1996.
  • Shirokorad, A, Rakety nad Morem, Second Edition, Tekhnika I Vooruzhenie, Moscow 11-12, 1997 via Dietrich Haeseler.
  • Siddiqi, Asif A, Soviet Space Web Page, 1999 via Dietrich Haeseler. Web Address when accessed: http://home.earthlink.net/~cliched/main_space.html.
Contact us with any corrections, additions, or comments.
Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.

© Mark Wade, 1997 - 2008 except where otherwise noted.